针对星际探测任务中燃料最省小推力转移轨道问题，提出一种基于标称轨道的快速设计方法。
A novel rapid method to design optimal-fuel interplanetary trajectory for low-thrust propulsion is presented based on normal trajectory approach.
针对近距离相对运动的轨道控制问题，提出用常值小推力完成最优转移的方法。
An optimal orbit maneuver method based on continuous low thrust was presented to solve relative motion control.
分析认为PPT是一种先进的小推力动力装置，特别适合于微小卫星的轨道转移、姿态控制、位置保持以及星座编队飞行。
It was showed that PPT was a kind of advanced propeller with small thrust, which was suitable to orbit transfer, attitude control, station keeping and formation flying for small and micro satellite.
首先，基于归一化的改进春分点根数建立了星际小推力转移轨道的优化模型；
First, the optimization model of interplanetary low-thrust trajectory was established using modified equinoctial elements.
首先，基于归一化的改进春分点根数建立了星际小推力转移轨道的优化模型；
First, the optimization model of interplanetary low-thrust trajectory was established using modified equinoctial elements.
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